An integrated radar reconnaissance payload device, radar equipment and unmanned aerial vehicle

Abstract

This application discloses an integrated radar reconnaissance payload device, radar equipment, and unmanned aerial vehicle (UAV). An upper housing, a lower housing, and an radome, together with a rear housing, form a closed cavity. Multiple heat pipes connect to the side of the rear housing near the radome, with one end of each heat pipe facing the radome. A first heat sink connects to at least one of the heat pipes and is also connected to the side of the upper housing near the lower housing. A first module is detachably connected to the first heat sink. A support body is detachably connected to the upper housing, with its bottom suspended within the closed cavity. A second module is detachably connected to the support body. A second heat sink connects to the lower housing. A third module is detachably connected to the lower housing. A fourth module is detachably connected to the side of the rear housing away from the radome. This application provides collision protection for each module and utilizes multiple heat pipes to conduct heat from the closed cavity through the upper housing, thereby further achieving a waterproof and heat-conducting effect for the module units.

Description

Technical Field

[0001] This application relates to the field of integrated radar reconnaissance payload devices, and more particularly to an integrated radar reconnaissance payload device, radar equipment, and unmanned aerial vehicle. Background Technology

[0002] Radar signal reconnaissance payloads utilize radar equipment to emit electromagnetic waves and receive the reflected echoes from targets to detect, identify, and locate them, playing a crucial role in electronic information systems. Radar payloads are widely used in vehicles, ships, and airborne applications for target reconnaissance in various scenarios.

[0003] With the continuous development of science and technology, radar reconnaissance payloads are gradually developing towards system networking and automation. The structure of radar reconnaissance payloads will be further optimized in the direction of serialization, miniaturization and integration of various configurations, and will continue to play an irreplaceable role in the reconnaissance field, providing technical support for national security and strategic decision-making.

[0004] Radar reconnaissance payloads are mounted on UAVs, which operate in harsh environments. If the radar's heat dissipation performance is poor, the electronic equipment will inevitably be affected under long-term operation. Summary of the Invention

[0005] The main purpose of this application is to provide an integrated radar reconnaissance payload device, radar equipment, and unmanned aerial vehicle, which aims to reduce the installation difficulty of the module unit and improve the waterproof and thermal conductivity performance of the module unit.

[0006] To achieve the above objectives, this application provides an integrated radar reconnaissance payload device, comprising: a rear housing, one side of which is detachably connected to an upper housing, a lower housing, and an radome, wherein the upper housing and the lower housing are both detachably connected to the radome, and the upper housing, the lower housing, the radome, and the rear housing form a closed cavity; multiple heat-conducting pipes connected to the side of the rear housing near the radome, with one end of each heat-conducting pipe facing the radome; a first heat dissipation plate connected to at least one of the multiple heat-conducting pipes, and the first heat dissipation plate connected to the side of the upper housing near the lower housing; a first module detachably connected to the first heat dissipation plate; a support body detachably connected to the upper housing, with its bottom suspended within the closed cavity; a second module detachably connected to the rear housing; a second heat dissipation plate connected to the lower housing; a third module detachably connected to the lower housing; and a fourth module detachably connected to the side of the rear housing away from the radome.

[0007] Optionally, the support body is a trapezoidal block, and a second connecting plate is connected to the side of the support body in sequence through a first connecting plate and a support column. The second connecting plate is connected to the upper housing. The side of the support body near the rear housing is connected to the second module through a third heat sink. At least one antenna unit is mounted on the side of the support body away from the second module through a first antenna mounting bracket. The two sides of the support body that are adjacent to and opposite to the first antenna mounting bracket and the second module are provided with second antenna mounting brackets, and each of the two second antenna mounting brackets is equipped with at least one antenna unit.

[0008] Optionally, the gaps between the upper housing, the lower housing, and the radome are sealed with sealing strips.

[0009] Optionally, a connector adapter plate is provided on the side of the rear housing away from the radome, and the connector adapter plate is connected to the connector.

[0010] Optionally, the third module is detachably connected to the lower housing via a third heat sink, and the fourth module is connected to the rear housing via a fourth heat sink. The first, second, third, and fourth heat sinks are all made of copper.

[0011] Optionally, the adjacent upper housing, lower housing, rear housing, and radome are connected by the sealing plate.

[0012] Optionally, the plurality of heat pipes are four in number. Two of the heat pipes are L-shaped and one end of each is welded side by side to the side of the rear housing, and the other end of each is welded to the first heat sink. The other two heat pipes are serpentine and one end of each of the two heat pipes is welded to the side of the rear housing, and the other end is suspended and faces the antenna cover.

[0013] Optionally, the upper housing, the lower housing, and the radome are all irregularly shaped arc surfaces.

[0014] In addition, to achieve the above objectives, this application also provides a radar device equipped with the integrated radar reconnaissance payload device provided in the above embodiments.

[0015] In addition, to achieve the above objectives, this application also provides a drone equipped with the radar device provided in the foregoing embodiments.

[0016] This application proposes an integrated radar reconnaissance payload device, radar equipment, and UAV. The rear housing is detachably connected to an upper housing, a lower housing, and an radome via one side of the rear housing. Both the upper and lower housings are detachably connected to the radome, and the upper housing, lower housing, and radome, together with the rear housing, form a closed cavity. Multiple heat pipes connect to the side of the rear housing near the radome, with one end of each heat pipe facing the radome. A first heat sink connects to at least one of the heat pipes and is connected to the side of the upper housing near the lower housing. A first module is detachably connected to the first heat sink. A support body is detachably connected to the upper housing, with its bottom suspended within the closed cavity. A second module is detachably connected to the support body. A second heat sink is connected to the lower housing. A third module is detachably connected to the lower housing. A fourth module is detachably connected to the side of the rear housing away from the radome. The upper housing, lower housing, and radome, together with the rear housing, form a closed cavity, which protects the internal modules. The multiple heat pipes dissipate heat from the closed cavity through the upper housing, achieving a waterproof and heat-conducting effect for the module units. Attached Figure Description

[0017] Figure 1 A schematic diagram of the sealed payload assembly structure provided for an embodiment of the integrated radar reconnaissance payload device of this application;

[0018] Figure 2 A schematic diagram of the disassembled structure of the sealed payload assembly provided in an embodiment of the integrated radar reconnaissance payload device of this application;

[0019] Figure 3 A schematic diagram of the disassembled housing assembly provided for an embodiment of the integrated radar reconnaissance payload device of this application;

[0020] Figure 4 A schematic diagram of the disassembled antenna support structure provided for an embodiment of the integrated radar reconnaissance payload device of this application;

[0021] Figure 5 This is a schematic diagram of the split structure of the heat conduction system provided for an embodiment of the integrated radar reconnaissance payload device of this application.

[0022] Explanation of reference numerals in the attached drawings: 1. Housing assembly; 11. Upper housing; 12. Lower housing; 13. Rear housing; 2. Antenna bracket; 21. Second connecting plate; 22. Bracket column; 23. First connecting plate; 24. Bracket body; 25. First antenna mounting bracket; 26. Second antenna mounting bracket; 3. Connector adapter plate; 31. Connector; 41. First module; 42. Second module; 43. Third module; 44. Fourth module; 51. Heat pipe; 52. First heat sink; 6. Antenna cover; 7. Antenna unit; 81. Sealing strip; 82. Sealing plate.

[0023] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0024] It should be understood that the specific embodiments described herein are merely illustrative of this application and are not intended to limit this application.

[0025] Reference Figure 1 The integrated radar reconnaissance payload device provided in the first embodiment of this application may include a rear housing 13, multiple heat pipes 51, a first heat sink 52, a first module 41, a support body 24, a second module 42, a second heat sink, a third module 43, and a fourth module 44. One side of the rear housing 13 is detachably connected to the upper housing 11, the lower housing 12, and the radome 6. Both the upper housing 11 and the lower housing 12 are detachably connected to the radome 6, and the upper housing 11, the lower housing 12, and the radome 6 form a closed cavity with the rear housing 13. Multiple heat pipes 51 are connected to the rear housing. 13 is located near the side of the radome 6, and one end of each of the multiple heat pipes 51 faces the radome 6; the first heat sink 52 is connected to at least one of the multiple heat pipes 51, and the first heat sink 52 is connected to the side of the upper housing 11 near the lower housing 12; the first module 41 is detachably connected to the first heat sink 52; the bracket body 24 is detachably connected to the upper housing 11, and its bottom is suspended in the closed cavity; the second module 42 is detachably connected to the rear housing 13; the second heat sink is connected to the lower housing 12; the third module 43 is detachably connected to the lower housing 12; the fourth module 44 is detachably connected to the side of the rear housing 13 away from the radome 6.

[0026] Specifically, the payload structure consists of three shell parts: upper, middle, and lower. The middle structure, with embedded heat pipes, divides the payload into two enclosed areas, front and rear. The upper shell serves as the primary air-cooled heat dissipation surface, bearing the majority of the heat from the module units introduced by the heat pipes. It should be noted that the first module 41, second module 42, third module 43, and fourth module 44 are all high-energy-consuming modules that generate significant heat during operation, thus requiring heat dissipation. Multiple heat pipes 51 connect to the side of the rear shell 13 near the radome 6, and each heat pipe 51 has one end welded to the shell 11. This allows for the dissipation of internal heat and the conduction of external low temperatures into the enclosed space, thereby cooling the first module 41, second module 42, and third module 43. The fourth module 44, attached to the back of the rear shell 13, can also dissipate heat through the multiple heat pipes 51. This design protects the internal modules from weathering and reduces the temperature inside the sealed cavity, effectively protecting the radar reconnaissance payload and extending its lifespan.

[0027] It is worth noting that this application can be installed in different positions on different housings using M4 screws, depending on the size and power consumption of the module unit. In other words, the position of the module unit can be arranged according to the specific wiring method, module size, power consumption and system heat dissipation method. This application does not impose too many restrictions here.

[0028] It is also worth noting that the connection in this application can be a fixed connection or a detachable connection. The fixed connection can be welding, integral molding, etc., and there are no restrictions here.

[0029] In the embodiments of this application, the support body 24 is a trapezoidal block. The side of the support body 24 is connected to a second connecting plate 21 through a first connecting plate 23 and a support column 22. The second connecting plate 21 is connected to the upper housing 11. The side of the support body 24 near the rear housing 13 is connected to the second module 42 through a third heat sink. At least one antenna element 7 is mounted on the side of the support body 24 away from the second module 42 through a first antenna mounting bracket 25. The two sides of the support body 24 that are adjacent to and opposite to the first antenna mounting bracket 25 and the second module 42 are provided with second antenna mounting brackets 26, and each of the two second antenna mounting brackets 26 is equipped with at least one antenna element 7.

[0030] refer to Figure 2 Specifically, the first antenna mounting bracket 25 is a circular plate, and the second antenna mounting bracket 26 is a square plate. The bracket body 24, the second connecting plate 21, the bracket column 22, the first connecting plate 23, the first antenna mounting bracket 25, and the second antenna mounting bracket 26 are connected as a single unit by screws to form the antenna bracket 2. The antenna bracket 2 has eight mounting slots for antenna elements 7 and reserved mounting positions for counterweight structures. The antenna elements 7 are fixed in the recessed grooves on the first antenna mounting bracket 25 and the second antenna mounting bracket 26 via SMA or SMP connectors, allowing for quick insertion and removal of the antenna elements 7. The first connecting plate 23, the bracket column 22, and the second connecting plate 21 are all made of Q690ME steel to maximize structural rigidity and ensure that the structural components are not easily deformed under vertical impact and vibration, thus preventing structural deformation and displacement from damaging the lower third module 43. The internal antenna elements and circuit modules of the load adopt a miniaturized design, and the direct-plug connection method facilitates assembly and disassembly.

[0031] In addition, the antenna bracket 2 is fixed to the upper housing 11. In addition to installing the antenna unit 7 and the counterweight, it can also have a built-in wiring area, which shortens the wiring length between the antenna unit and other modules and solves the problem of reduced antenna unit performance due to long wiring.

[0032] refer to Figure 3In the embodiments of this application, the gaps between the upper housing 11, the lower housing 12, and the radome 6 are sealed by a sealing strip 81, and the gaps between the upper housing 11, the lower housing 12 or the radome 6 and the rear housing 13 are sealed by a sealing plate 82.

[0033] The housing assembly 1 consists of three parts: upper housing 11, lower housing 12, and rear housing 13, which are connected as one unit by screws. Each housing contact surface has a special groove for sealing strip 81 to block external rainwater erosion, greatly reducing the economic and time costs of machining. At the same time, the screw connection method is convenient to operate and easy to install.

[0034] For example, this application can cut out a corresponding sealing plate 82 according to the shape of the contact surface between the radome 6 and the housing assembly 1, ensuring that the sealing plate 82 perfectly fits the contact surface. The radome 6 can be connected to the housing assembly 1 by M1.8 screws to press the sealing plate 82 firmly, thereby ensuring the sealing performance of the load device.

[0035] It should be noted that the model and thickness of the sealing plate 82 need to be selected according to the actual situation. In this application, silicone rubber plate 04-22-1319-GXJ / AC is selected as the sealing plate 82.

[0036] Continue to refer to Figure 1 In the embodiments of this application, a connector adapter plate 3 is provided on the side of the rear housing 13 away from the antenna cover 6, and the connector adapter plate 3 is connected to the connector 31.

[0037] The connector 31 is fixed to the connector adapter plate 3, which is then fixed to the housing assembly 1 with M2 screws. It is worth noting that the front area of ​​the load device includes multiple antenna units 7, various high-power module units, a sealing plate 82, an antenna bracket 2, and an radome 6. The radome 6 presses against the upper, middle, and lower housings to form a front enclosed area. The connector adapter plate 3 is screwed onto the rear surface of the rear housing 13 to form a rear enclosed area, where the fourth module 44 is located.

[0038] Continue to refer to Figure 1 In the embodiments of this application, the third module 43 is detachably connected to the lower housing 12 via a third heat sink, and the fourth module 44 is connected to the rear housing 13 via a fourth heat sink. The first heat sink 52, the second heat sink, the third heat sink, and the fourth heat sink are all copper heat sinks. Copper heat sinks have high thermal conductivity and can quickly exchange heat.

[0039] Specifically, the edges of the upper housing 11, lower housing 12, radome 6 and rear housing 13 are all provided with grooves, and the grooves between adjacent upper housing 11, lower housing 12, rear housing 13 and radome 6 are connected by sealing strips 81.

[0040] refer to Figure 4 In the embodiments of this application, there are four heat pipes 51. Two heat pipes 51 are L-shaped and one end of each is welded to the side of the rear housing 13, and the other end of each is welded to the first heat sink 52. The other two heat pipes 51 are serpentine and one end of each of the two heat pipes 51 is welded to the side of the rear housing 13, and the other end is suspended and faces the antenna cover 6.

[0041] The multiple heat pipes 51 are designed with an irregular shape to conduct heat from the sealed structure to the upper shell. Specifically, after the first heat sink 52 is welded to the shell assembly 1, the first heat sink 52 is welded to the upper surface of the heat pipes 51 as a single unit. The first module 41 is attached to the surface of the first heat sink 52 with M3 screws, which evenly distributes heat and increases the contact area. The heat pipes 51 transfer heat from the sealed load structure to the outer surface of the shell, where it is cooled by air, thus achieving heat dissipation within the sealed space.

[0042] refer to Figure 5 In the embodiments of this application, the upper housing 11, the lower housing 12, and the radome 6 are all irregularly shaped arc surfaces. These arc surfaces reduce air resistance during flight and increase heat dissipation surface area. The payload device adopts a split design, dividing the difficult-to-machine irregular arc into three parts, facilitating installation and processing, and reducing machining time and manufacturing costs.

[0043] Based on the above embodiments, this application also provides a radar device equipped with the integrated radar reconnaissance payload device provided in the above embodiments.

[0044] Based on the above embodiments, this application also provides a drone equipped with the radar device provided in the foregoing embodiments.

[0045] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. An integrated radar reconnaissance payload device, characterized in that, include: The rear housing (13) is detachably connected to the upper housing (11), the lower housing (12) and the radome (6) on one side. The upper housing (11) and the lower housing (12) are both detachably connected to the radome (6), and the upper housing (11), the lower housing (12) and the radome (6) together with the rear housing (13) form a closed cavity. Multiple heat pipes (51) are connected at one end to the side of the rear housing (13) near the antenna cover (6), and the other end of each of the multiple heat pipes (51) faces the antenna cover (6) and is welded to the upper housing (11). The first heat sink (52) is connected to at least one of the multiple heat pipes (51), and the first heat sink (52) is disposed on the side of the upper housing (11) near the lower housing (12); The first module (41) is detachably connected to the first heat sink (52); The bracket body (24) is detachably connected to the upper housing (11). The second module (42) is detachably connected to the rear housing (13). The second heat sink is connected to the lower housing (12). The third module (43) is detachably connected to the lower housing (12); The fourth module (44) is detachably connected to the side of the rear housing (13) away from the radome (6).

2. The integrated radar reconnaissance payload device as described in claim 1, characterized in that, The main body (24) of the support is a trapezoidal block. The side of the main body (24) is connected to the second connecting plate (21) through the first connecting plate (23) and the support column (22) in sequence. The second connecting plate (21) is connected to the upper shell (11). The side of the bracket body (24) near the rear housing (13) is connected to the second module (42) via a third heat sink. At least one antenna unit (7) is mounted on the side of the support body (24) away from the second module (42) via the first antenna mounting bracket (25). Two second antenna mounting brackets (26) are provided on both sides of the bracket body (24) which are adjacent to and opposite to the first antenna mounting bracket (25) and the second module (42), and at least one antenna unit (7) is installed on each of the two second antenna mounting brackets (26).

3. The integrated radar reconnaissance payload device as described in claim 1, characterized in that, The gaps between the upper housing (11), the lower housing (12) and the radome (6) are sealed by sealing strips (81).

4. The integrated radar reconnaissance payload device as described in claim 1, characterized in that, The rear housing (13) has a connector adapter plate (3) on one side away from the antenna cover (6), and the connector adapter plate (3) is connected to the connector (31).

5. The integrated radar reconnaissance payload device as described in claim 1, characterized in that, The third module (43) is detachably connected to the lower housing (12) via the third heat sink, and the fourth module (44) is connected to the rear housing (13) via the fourth heat sink. The first heat sink (52), the second heat sink, the third heat sink, and the fourth heat sink are all copper heat sinks.

6. The integrated radar reconnaissance payload device as described in claim 3, characterized in that, The adjacent upper housing (11), lower housing (12), rear housing (13) and radome (6) are connected by a sealing plate (82).

7. The integrated radar reconnaissance payload device as described in claim 1, characterized in that, The multiple heat pipes (51) consist of four tubes. Two of the heat pipes (51) are L-shaped and one end of each is welded to the side of the rear housing (13) in parallel. The other end of each of them is welded to the first heat sink (52). The other two heat pipes (51) are serpentine and one end of each of the two heat pipes (51) is welded to the side of the rear housing (13). The other end of each of them is welded to the upper housing (11).

8. The integrated radar reconnaissance payload device as described in claim 1, characterized in that, The upper housing (11), the lower housing (12), and the radome (6) are all irregularly shaped arc surfaces.

9. A radar device, characterized in that, It is equipped with an integrated radar reconnaissance payload device as described in any one of claims 1-8.

10. A drone, characterized in that, It is equipped with the radar device as described in claim 9.

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